U.S. patent number 10,508,556 [Application Number 14/761,841] was granted by the patent office on 2019-12-17 for rotor blade root spacer with grip element.
This patent grant is currently assigned to United Technologies Corporation. The grantee listed for this patent is United Technologies Corporation. Invention is credited to Lee Drozdenko, James H. Moffitt.
United States Patent |
10,508,556 |
Drozdenko , et al. |
December 17, 2019 |
Rotor blade root spacer with grip element
Abstract
An assembly includes a rotor disk, a rotor blade and a root
spacer. The rotor disk includes a slot that extends longitudinally
into the rotor disk. The rotor blade includes a blade root arranged
within the slot. The root spacer is arranged with the slot between
the rotor disk and the blade root. The root spacer extends
longitudinally to a spacer end, and includes a grip element and a
plurality of notches. The grip element is arranged at the spacer
end laterally between the notches. The grip element at least
partially defines the notches. The notches extend radially and
longitudinally into the root spacer.
Inventors: |
Drozdenko; Lee (Bristol,
CT), Moffitt; James H. (Manchester, CT) |
Applicant: |
Name |
City |
State |
Country |
Type |
United Technologies Corporation |
Hartford |
CT |
US |
|
|
Assignee: |
United Technologies Corporation
(Farmington, CT)
|
Family
ID: |
51209960 |
Appl.
No.: |
14/761,841 |
Filed: |
January 17, 2013 |
PCT
Filed: |
January 17, 2013 |
PCT No.: |
PCT/US2013/021935 |
371(c)(1),(2),(4) Date: |
July 17, 2015 |
PCT
Pub. No.: |
WO2014/113009 |
PCT
Pub. Date: |
July 24, 2014 |
Prior Publication Data
|
|
|
|
Document
Identifier |
Publication Date |
|
US 20150361805 A1 |
Dec 17, 2015 |
|
Current U.S.
Class: |
1/1 |
Current CPC
Class: |
F01D
5/02 (20130101); B25B 7/02 (20130101); F01D
25/285 (20130101); B25B 7/08 (20130101); F01D
5/326 (20130101); F01D 5/3007 (20130101); F01D
5/3092 (20130101); F01D 5/30 (20130101); F01D
15/12 (20130101); F01D 5/12 (20130101); F05D
2220/30 (20130101) |
Current International
Class: |
F01D
5/32 (20060101); F01D 5/02 (20060101); F01D
25/28 (20060101); F01D 5/30 (20060101); F01D
5/12 (20060101); F01D 15/12 (20060101); B25B
7/02 (20060101); B25B 7/08 (20060101) |
Field of
Search: |
;416/220R,221,248 |
References Cited
[Referenced By]
U.S. Patent Documents
Foreign Patent Documents
Other References
EP Search Report dated Feb. 10, 2016. cited by applicant.
|
Primary Examiner: Laurenzi; Mark A
Assistant Examiner: Thiede; Paul W
Attorney, Agent or Firm: O'Shea Getz P.C.
Claims
What is claimed is:
1. An assembly with an axis, comprising: a rotor disk including a
slot that extends axially into the rotor disk; a rotor blade
including a blade root arranged within the slot; and a root spacer
arranged with the slot between the rotor disk and the blade root,
the root spacer extending axially to a spacer end and including a
grip element and a plurality of notches; wherein the grip element
is arranged at the spacer end circumferentially between the
notches, and at least partially defines the notches; wherein at
least one of the notches has an open end at the spaces end
positioned intermediate outbound edges of the root spacer and the
at least one of the notches extends radially and axially into the
root spacer and one of the notches extends circumferentially within
the root spacer; wherein the grip element includes a base and a
flange that extends circumferentially from the base; and wherein
the base and the flange at least partially define a first one of
the notches.
2. The assembly of claim 1, wherein each of the notches extends
circumferentially within the root spacer.
3. The assembly of claim 1, wherein a first one of the notches
extends radially through the root spacer.
4. The assembly of claim 1, wherein a first one of the notches
extends radially into the root spacer to a surface.
5. The assembly of claim 1, wherein the flange comprises a first
flange, and the grip element further includes a second flange that
extends circumferentially from the base; the base is arranged
circumferentially between the first flange and the second flange;
and the base and the second flange at least partially define a
second one of the notches.
6. The assembly of claim 1, wherein the grip element is axially
recessed from the spacer end.
7. The assembly of claim 1, wherein the slot extends axially into
the rotor disk from a disk end; and the spacer end is arranged at
the disk end.
8. The assembly of claim 1, wherein the blade root extends axially
to a root end; and the spacer end is approximately axially aligned
with the root end.
9. The assembly of claim 1, wherein the slot is one of a plurality
of slots that extend axially into the rotor disk; the rotor blade
is one of a plurality of rotor blades arranged circumferentially
around the axis, and each of the rotor blades includes a blade root
arranged within a respective one of the slots; and the root spacer
is one of a plurality of root spacers, each of the root spacers is
arranged within a respective one of the slots between the rotor
disk and a respective one of the blade roots, and at least a
plurality of the root spacers each include a grip element.
10. The assembly of claim 1, wherein the rotor blade comprises a
turbine engine fan blade.
11. The assembly of claim 1, further comprising: a plurality of
turbine engine rotors arranged along the axis and including a first
rotor and a second rotor, wherein one of the engine rotors includes
the rotor disk, the rotor blade and the root spacer; and a gear
train that connects the first rotor to the second rotor.
12. The assembly of claim 11, wherein the first rotor comprises a
fan rotor that includes the rotor disk, the rotor blade and the
root spacer.
13. An assembly with an axis, comprising: a rotor disk including a
slot that extends axially into the rotor disk; a rotor blade
including a blade root arranged within the slot; and a root spacer
arranged with the slot between the rotor disk and the blade root,
the root spacer extending axially to a spacer end and including a
grip element and a plurality of notches; wherein the grip element
is arranged at the spacer end circumferentially between the
notches, and at least partially defines the notches; wherein at
least one of the notches has an open end at the spacer end
positioned intermediate outbound edges of the root spacer and the
at least one of the notches extends radially and axially into the
root spacer, and one of the notches extends circumferentially
within the root spacer; and wherein the grip element extends
axially to the spacer end.
14. An assembly with an axis, comprising: a rotor disk including a
slot that extends axially into the rotor disk; a rotor blade
including a blade root arranged within the slot; and a root spacer
arranged with the slot between the rotor disk and the blade root,
the root spacer extending axially to a spacer end and including a
grip element and a plurality of notches; wherein the grip element
is arranged at the spacer end circumferentially between the
notches, and at least partially defines the notches; wherein at
least one of the notches has an open end at the spacer end
positioned intermediate outbound edges of the root spacer and the
at least one of the notches extends radially and axially into the
root spacer, and one of the notches extends circumferentially
within the root spacer; wherein the root spacer includes an inner
surface and an outer surface; wherein the inner surface is
positioned next to the rotor disk; wherein the outer surface is
positioned next to the blade root; and wherein the root spacer is
configured as a solid monolithic body such that material of the
root spacer extends uninterrupted between the inner surface and the
outer surface.
15. An assembly disposed along a longitudinal axis, comprising: a
rotor disk including a slot that extends axially into the rotor
disk; a rotor blade including a blade root arranged within the
slot; and a root spacer formed of a single layer of material being
axially arranged with the slot between the rotor disk and the blade
root, the root spacer including an axial spacer end and at least
two axial portions, the at least two axial portions including a
generally planar spacer base portion in communication with one or
more spacer side portions, the one or more spacer side portions
each having an angularly disposed, non-parallel relationship to the
spacer base portion, the spacer base portion generally disposed
parallel to the longitudinal axis, and the spacer base portion
including a grip element and defining a plurality of notches;
wherein the grip element is arranged in the spacer base portion at
the axial spacer end, the grip element is circumferentially between
the plurality of notches, and the grip element at least partially
defines each notch of the plurality of notches; and wherein each
notch of the plurality of notches extends radially and axially into
the spacer base portion of the root spacer, and at least one of the
plurality of notches extends circumferentially within the spacer
base portion of the root spacer.
Description
This application claims priority to PCT Patent Application No.
PCT/US13/21935 filed Jan. 17, 2013, which is hereby incorporated by
reference.
BACKGROUND OF THE INVENTION
1. Technical Field
This disclosure relates generally to rotational equipment and, more
particularly, to a root spacer for arranging between a rotor disk
and a root of a rotor blade.
2. Background Information
A fan assembly for a typical turbine engine includes a plurality of
fan blades arranged circumferentially around a rotor disk. Each of
the fan blades includes an airfoil connected to a dovetail root.
The root is inserted into a respective dovetail slot within the
rotor disk, and connects the fan blade to the rotor disk. A radial
height of the root is typically less than a radial height of the
slot. A gap therefore extends between a radial inner surface of the
root and a radial inner surface of the rotor disk within the slot.
Such a gap is typically filled with a root spacer, which is
sometimes also referred to as a fan blade spacer.
A typical root spacer is configured to reduce slippage and wear
between the root and the rotor disk where centrifugal loading on
the fan blade is relatively low; e.g., during wind milling. By
filling the gap, for example, the root spacer reduces space that
would otherwise be available for rotating of the root within the
slot.
Various types and configurations of root spacers are known in the
art. One such root spacer includes a threaded hole that extends
into an end of the spacer. During engine maintenance, a tool with a
threaded shaft is threaded into the hole and manipulated to pull
the root spacer from the slot. The root spacer therefore has a
relatively large radial thickness in order to accommodate the
threaded hole. Such a relatively large radial thickness may
increase the overall size and/or weight of the fan assembly as well
as take away space that would otherwise be available for a larger
blade root.
There is a need in the art for an improved root spacer.
SUMMARY OF THE DISCLOSURE
According to an aspect of the invention, an assembly is provided
that includes a rotor disk, a rotor blade and a root spacer. The
rotor disk includes a slot that extends longitudinally into the
rotor disk. The rotor blade includes a blade root arranged within
the slot. The root spacer is arranged with the slot between the
rotor disk and the blade root. The root spacer extends
longitudinally to a spacer end, and includes a grip element and a
plurality of notches. The grip element is arranged at the spacer
end laterally between the notches, and at least partially defines
the notches. The notches extend radially and longitudinally into
the root spacer, and at least one of the notches extends laterally
within the root spacer.
According to another aspect of the invention, another assembly is
provided that includes a rotor disk, a rotor blade and a root
spacer. The rotor disk includes a slot that extends longitudinally
into the rotor disk. The rotor blade includes a blade root arranged
within the slot. The blade root extends longitudinally to a root
end. The root spacer is arranged with the slot between the rotor
disk and the blade root. The root spacer extends longitudinally to
a spacer end that is approximately longitudinally aligned with the
root end. The root spacer includes a grip element and a plurality
of notches. The grip element is arranged at the spacer end
laterally between the notches, and at least partially defines the
notches. The notches extend radially and longitudinally into the
root spacer.
A first of the notches may extend laterally within the root spacer.
Alternatively, each of the notches may extend laterally within the
root spacer.
A first of the notches may extend laterally into the root spacer.
Alternatively, each of the notches may extend laterally into the
root spacer.
A first of the notches may extend radially through the root spacer.
Alternatively, each of the notches may extend radially through the
root spacer.
A first of the notches may extend radially into the root spacer to
a surface. Alternatively, each of the notches may extend radially
into the root spacer to a surface.
The grip element may include a base and a flange that extends
laterally from the base. The base and the flange may at least
partially define a first of the notches. The flange may be a first
flange, and the grip element may also include a second flange that
extends laterally from the base. The base may be arranged laterally
between the first and the second flanges. The base and the second
flange may at least partially define a second of the notches.
The grip element may extend longitudinally to the spacer end.
Alternatively, the grip element may be longitudinally recessed from
the spacer end.
The slot may extend longitudinally into the rotor disk from a disk
end. The spacer end may be arranged at the disk end. Alternatively,
the spacer end may be approximately longitudinally aligned with the
disk end.
The blade root may extend longitudinally to a root end. The spacer
end may be approximately longitudinally aligned with the root
end.
The slot may be one of a plurality of slots that extend
longitudinally into the rotor disk. The rotor blade may be one of a
plurality of rotor blades arranged circumferentially around an
axis. Each of the rotor blades may include a blade root arranged
within a respective one of the slots. The root spacer may be one of
a plurality of root spacers. Each of the root spacers may be
arranged within a respective one of the slots between the rotor
disk and a respective one of the blade roots. At least some or all
of the root spacers each include a grip element.
The rotor blade may be configured as or include a turbine engine
fan blade. Alternatively, the rotor blade may be configured as or
include any other type of turbine engine blade.
The assembly may include a gear train and a plurality of turbine
engine rotors arranged along an axis. The engine rotors may include
a first rotor and a second rotor. One of the engine rotors may
include the rotor disk, the rotor blade and the root spacer. The
gear train may connect the first rotor to the second rotor. The
first rotor may be configured as or include a fan rotor, and may
include the rotor disk, the rotor blade and the root spacer.
The foregoing features and the operation of the invention will
become more apparent in light of the following description and the
accompanying drawings.
BRIEF DESCRIPTION OF THE DRAWINGS
FIG. 1 is a side cutaway illustration of a geared turbine
engine;
FIG. 2 is a perspective illustration of a partially assembled rotor
assembly;
FIG. 3 is a side sectional illustration of a portion of the rotor
assembly of FIG. 2;
FIG. 4 is a partial illustration of an end of the rotor assembly of
FIG. 2;
FIG. 5 is an illustration of a root spacer for the rotor assembly
of FIG. 2;
FIG. 6 is a perspective illustration of an end portion of the root
spacer of FIG. 5;
FIG. 7 is a partial illustration of an end of another root spacer
for the rotor assembly of FIG. 2;
FIG. 8 is an illustration of a tool for removing a root spacer from
a slot of a rotor disk;
FIG. 9 is an illustration of an end portion of another root spacer
for the rotor assembly of FIG. 2;
FIG. 10 is an illustration of an end portion of another root spacer
for the rotor assembly of FIG. 2; and
FIG. 11 is an illustration of an end portion of another root spacer
for the rotor assembly of FIG. 2.
DETAILED DESCRIPTION OF THE INVENTION
FIG. 1 is a side cutaway illustration of a geared turbine engine 20
that extends along an axis 22 between an upstream airflow inlet 24
and a downstream airflow exhaust 26. The engine 20 includes a fan
section 28, a compressor section 29, a combustor section 30 and a
turbine section 31. The compressor section 29 includes a low
pressure compressor (LPC) section 29A and a high pressure
compressor (HPC) section 29B. The turbine section 31 includes a
high pressure turbine (HPT) section 31A and a low pressure turbine
(LPT) section 31B. The engine sections 28-31 are arranged
sequentially along the axis 22 within an engine housing 34, which
includes a first engine case 36 (e.g., a fan nacelle) and a second
engine case 38 (e.g., a core nacelle).
Each of the engine sections 28, 29A, 29B, 31A and 31B includes a
respective rotor 40-44. Each of the rotors 40-44 includes a
plurality of rotor blades arranged circumferentially around and
connected to (e.g., formed integral with or mechanically fastened,
welded, brazed or otherwise adhered to) one or more respective
rotor disks. The fan rotor 40 is connected to a gear train 46;
e.g., an epicyclic gear train. The gear train 46 and the LPC rotor
41 are connected to and driven by the LPT rotor 44 through a low
speed shaft 48. The HPC rotor 42 is connected to and driven by the
HPT rotor 43 through a high speed shaft 50. The low and high speed
shafts 48 and 50 are rotatably supported by a plurality of bearings
52. Each of the bearings 52 is connected to the second engine case
38 by at least one stator such as, for example, an annular support
strut.
Air enters the engine 20 through the airflow inlet 24, and is
directed through the fan section 28 and into an annular core gas
path 54 and an annular bypass gas path 56. The air within the core
gas path 54 may be referred to as "core air". The air within the
bypass gas path 56 may be referred to as "bypass air" or "cooling
air". The core air is directed through the engine sections 29-31
and exits the engine 20 through the airflow exhaust 26. Within the
combustion section 30, fuel is injected into and mixed with the
core air and ignited to provide forward engine thrust. The bypass
air is directed through the bypass gas path 56 and out of the
engine 20 to provide additional forward engine thrust or reverse
thrust via a thrust reverser. The bypass air may also be utilized
to cool various turbine engine components within one or more of the
engine sections 29-31.
FIG. 2 is a perspective illustration of a partially assembled rotor
assembly 58 for one of the rotors 40-44; e.g., the fan rotor 40.
This rotor assembly 58 includes a rotor disk 60, one or more rotor
blades 62 (e.g., fan blades), and one or more root spacers 64
(e.g., fan blade spacers).
The rotor disk 60 extends axially along the axis 22 between an
upstream disk end 66 and a downstream disk end 68. The rotor disk
60 extends radially out to a disk outer surface 70. The rotor disk
60 includes one or more slots 72 (e.g., dovetail slots) arranged
circumferentially around the axis 22. Referring to FIG. 3, one or
more of the slots 72 each extends longitudinally (e.g., axially)
into the rotor disk 60; e.g., through the rotor disk 60 between the
disk ends 66 and 68. Referring now to FIG. 4, one or more of the
slots 72 each extends radially into the rotor disk 60 from the
outer surface 70 to a slot base surface 74. One or more of the
slots 72 each extends laterally (e.g., circumferentially or
tangentially) between opposing slot side surfaces 76 and 78. The
base surface 74 extends laterally between the side surfaces 76 and
78.
Referring to FIG. 3, one or more of the rotor blades 62 each
includes a blade root 80 and an airfoil 82. The blade root 80
extends longitudinally between an upstream root end 84 and a
downstream root end 86. Referring now to FIG. 4, the blade root 80
includes a root base portion 88 and a pair of root side portions 90
and 92. The base portion 88 extends radially between the airfoil 82
and a root base surface 94. The side portions 90 and 92
respectively extend laterally from the base portion 88 to opposing
root side surfaces 96 and 98. The base surface 94 extends laterally
between the side surfaces 96 and 98.
Referring to FIGS. 4 to 6, one or more of the root spacers 64 each
extends longitudinally between an upstream spacer end 100 and a
downstream spacer end 102. One or more of the root spacers 64 each
includes a spacer base portion 104, one or more spacer side
portions 106 and 107, a grip element 108 (e.g., a T-shaped
protrusion), and one or more notches 110 and 112 (e.g., L-shaped
channels). The base and the side portions 104, 106 and 107 extend
radially between a spacer inner surface 114 and a spacer outer
surface 116. The base portion 104 extends laterally between the
side portions 106 and 107, and has a chord 118 (see FIG. 4). The
side portions 106 and 107 respectively extend laterally from the
base portion 104 to opposing spacer sides 120 and 122. Each of the
side portions 106 and 107 has a chord 124 (see FIG. 4) that may be
angularly offset from the chord 118 by, for example, between about
135 and about 160 degrees.
Referring to FIGS. 5 and 6, the grip element 108 is arranged at
(e.g., adjacent, proximate or on) the spacer end 100 laterally
between the notches 110 and 112. The grip element 108 includes a
base 126 and one or more flanges 128 and 130. The base 126 extends
longitudinally to the spacer end 100, and is arranged laterally
between the flanges 128 and 130. The flanges 128 and 130
respectively extend laterally from the base 126 to opposing grip
sides. The base 126 and the first flange 128 at least partially
define the first notch 110. The first notch 110, for example,
extends laterally within the root spacer 64 between a notch first
side surface 132 of the base portion 104 and the base 126 and the
first flange 128. The base 126 and the second flange 130 at least
partially define the second notch 112. The second notch 112, for
example, extends laterally within the root spacer 64 between a
notch second side surface 134 of the base portion 104 and the base
126 and the second flange 130. The notches 110 and 112 respectively
extend longitudinally into the root spacer 64 to notch end surfaces
136 and 138 of the base portion 104. One or more of the notches 110
and 112 extend radially through the root spacer 64 between the
inner surface 114 and the outer surface 116, which may enable the
root spacer 64 to have a relatively thin radial thickness.
Alternatively, referring to FIG. 7, one or more of the notches 110
and 112 may respectively extend radially into the root spacer 64'
to notch inner surfaces 140 and 142 (or notch outer surfaces).
Referring to FIG. 2, the rotor blades 62 are arranged
circumferentially around the axis 22. The blade roots 80 and the
root spacers 64 are respectively arranged within the slots 72.
Referring to FIG. 3, the spacer end 100 and the root end 84 may be
substantially longitudinally aligned and/or respective arranged at
the disk end 66. Alternatively, the spacer end 100 and/or the root
end 84 may be substantially longitudinally aligned with the disk
end 66. The spacer end 102 and the root end 86 may also or
alternatively be substantially longitudinally aligned and/or
respective arranged at the disk end 68. Alternatively, the spacer
end 102 and/or the root end 86 may be substantially longitudinally
aligned with the disk end 68. Referring to FIG. 4, the root side
portions 90 and 92 extend laterally between the root base portion
88 and the rotor disk 60. The root side surfaces 96 and 98 may
respectively engage (e.g., contact) the slot side surfaces 76 and
78. The root spacer 64 is arranged radially between the blade root
80 and the rotor disk 60. The spacer outer surface 116 may engage
one or more of the surfaces 94, 96 and 98, and/or the spacer inner
surface 114 may engage the slot base surface 74.
Referring to FIGS. 4, 6 and 8, a tool 144 with clamping grip
members 146 and 148 may be mated with the grip element 108 during
engine maintenance to remove the root spacer 64 from a respective
slot 72. The grip members 146 and 148, for example, may be
respectively inserted into the notches 110 and 112 and clamped
against the grip base 126. The tool 144 may subsequently be
manipulated to longitudinally pull the root spacer 64 out of the
slot 72. One or more of the grip members 146 and 148 may be coated
with a soft material such as rubber to provide a buffer between the
grip members 146 and 148 and the blade root 80 and/or the rotor
disk 60. One or more of the grip members 146 and 148 may also or
alternatively be coated with various other materials, or may be
uncoated.
FIG. 9 illustrates an end 150 of another root spacer 152 for the
rotor assembly 58 of FIG. 2. In contrast to the root spacer 64 of
FIG. 5, a grip element 156 of the root spacer 152 is longitudinally
recessed from the spacer end 150.
FIG. 10 illustrates an end 158 of another root spacer 160 for the
rotor assembly 58 of FIG. 2. In contrast to the root spacer 64 of
FIG. 5, one or more of the notches 110'' and 112'' of the root
spacer 160 extends laterally into the root spacer 160. The first
notch 110'', for example, extends laterally through the side
portion 106'' and into the base portion 104'' to the grip element
108. The second notch 112'' extends laterally through the side
portion 107'' and into the base portion 104'' to the grip element
108. The notch end surfaces 136'' and 138'' therefore respectively
form end surfaces of the side portions 106'' and 107''.
FIG. 11 illustrates an end 162 of another root spacer 164 for the
rotor assembly 58 of FIG. 2. In contrast to the root spacer 64 of
FIG. 5, a grip element 166 of the root spacer 164 is configured
without the flanges 128 and 130 shown in FIGS. 5 and 6. The notches
110''' and 112''' therefore are respectively laterally defined
between the side surfaces 132 and 134 and the base 126'''.
In some embodiments, one or more of the root spacers may be
constructed from a polymeric material such as plastic. In other
embodiments, one or more of the root spacers may be constructed
from metal. The present invention, however, is not limited to any
particular root spacer materials.
The slots, the blade roots, the root spacers, the grip elements and
the notches may have various configurations other than those
described above and illustrated in the drawings. For example, the
root spacer may include one or more channels, slots, dimples,
through-holes, etc. that may reduce the weight of the root spacer
and/or conform to an alternate embodiment root and/or slot
configuration. The grip member may be configured as an L-shaped
protrusion, or any other type of protrusion. The notches may be
defined by one or more arcuate surfaces. The present invention
therefore is not limited to any particular rotor disk, rotor blade
or root spacer types or configurations.
The terms "upstream", "downstream", "inner" and "outer" are used to
orientate the components of the rotor assembly described above
relative to the turbine engine and its axis. A person of skill in
the art will recognize, however, one or more of these components
may be utilized in other orientations than those described above.
For example, the grip element may be arranged at the downstream end
of the rotor disk. The present invention therefore is not limited
to any particular rotor assembly spatial orientations.
A person of skill in the art will recognize the rotor assembly may
be included in various turbine engines other than the one described
above as well as in other types of rotational equipment. The rotor
assembly, for example, may be included in a geared turbine engine
where a gear train connects one or more shafts to one or more
rotors in a fan section and/or a compressor section. Alternatively,
the rotor assembly may be included in a turbine engine configured
without a gear train. The rotor assembly may be included in a
turbine engine configured with a single spool, with two spools as
illustrated in FIG. 1, or with more than two spools. The present
invention therefore is not limited to any particular types or
configurations of turbine engines or rotational equipment.
While various embodiments of the present invention have been
disclosed, it will be apparent to those of ordinary skill in the
art that many more embodiments and implementations are possible
within the scope of the invention. For example, the present
invention as described herein includes several aspects and
embodiments that include particular features. Although these
features may be described individually, it is within the scope of
the present invention that some or all of these features may be
combined within any one of the aspects and remain within the scope
of the invention. Accordingly, the present invention is not to be
restricted except in light of the attached claims and their
equivalents.
* * * * *